Turbine engine guide vane and arrays thereof
An exit guide vane array for a turbine engine includes a set of guide vanes 28 having a solidity and defining fluid flow passages 74 with a chordwisely converging forward portion 80. The high solidity and convergent passage portion 80 resist fluid separation. The vanes may also cooperate with each other to restrict an observer's line of sight to planes upstream of the vane array.
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This invention was made under U.S. Government Contract N-00019-02-C-3003. The Government has certain rights in the invention.
TECHNICAL FIELDThis invention relates to exit guide vanes and arrays thereof for turbine engines and particularly to a vane array that exhibits good aerodynamic performance across a spectrum of operating conditions and that interrupts an observer's line of sight to components upstream of the vanes.
BACKGROUND OF THE INVENTIONAircraft turbine engines include a turbine module for extracting energy from a fluid stream comprising hot, gaseous products of combustion. The turbine module includes one or more arrays of blades and one or more arrays of vanes. Each blade array comprises multiple blades projecting radially outwardly from a rotatable hub. One array of guide vanes resides aft of the aftmost array of blades. These vanes are referred to as exit guide vanes. During engine operation, the fluid stream flows through the turbine module causing each blade array and its associated hub to rotate about a rotational axis. The rotating blades impart a substantial circumferential velocity component or swirl to the fluid stream, which reduces the thrust output of the engine. The fluid stream discharging from the aftmost array of blades flows through the array of exit guide vanes which deswirls the fluid, causing it to flow in a substantially axial direction thereby restoring thrust output that would otherwise be lost.
Ideally, the exit guide vanes must satisfy several requirements. One requirement, as noted above, is to turn or deswirl the combustion gases coming off the aftmost array of blades so that the gases exit the turbine module in a substantially axial direction. Second, the guide vanes must be able to tolerate changes in the incidence angle of the oncoming gas stream. The incidence angle depends on the circumferential component of velocity imparted to the fluid stream by the blades. This component varies considerably as a function of engine power. In particular, the guide vanes must be able to capture and redirect the gas stream across a wide range of incidence angles without being susceptible to aerodynamic separation and the attendant aerodynamic losses. A third requirement is that the guide vane array must have enough flow capacity to accept the full volume of combustion gases delivered to it. Otherwise the guide vane array would choke the flow through the turbine resulting in a shortfall in thrust. Fourth, in some military applications it is desirable for the guide vanes to block or interrupt an external observer's line of sight to the hot, rotating blades. This helps make the engine and its host aircraft less conspicuous to radar and infrared detection equipment.
It is difficult to concurrently satisfy all these requirements with conventional vanes. A vane having a conventional airfoil cross-section benefits from a large leading edge radius and large leading edge wedge angle which allow the vane to tolerate a wide range of incidence angles without being susceptible to fluid separation. However the large radius and wedge angle constrain the flow capacity of the vane array. Flow capacity can be restored by using a smaller quantity of vanes, however doing so can establish a line of sight to the hot blades, making the engine and its host aircraft vulnerable to detection. The line of sight can be interrupted by using wide chord vanes, but such vanes have the disadvantage of introducing undesirable weight, possibly even more weight than was saved by reducing the quantity of vanes. Alternatively, the line of sight can be interrupted by using highly cambered vanes. However an individual highly cambered vane is susceptible to aerodynamic separation, and an array of such vanes may not have adequate flow capacity.
It may also be possible to satisfy the conflicting requirements by employing variable pitch angle vanes, however this has the considerable disadvantage of introducing additional weight, cost and complexity into the engine.
What is needed is a simple, light weight vane array that exhibits satisfactory aerodynamic performance across a spectrum of operating conditions and that interrupts an observer's line of sight to components residing upstream of the vanes.
SUMMARY OF THE INVENTIONAccording to one embodiment of the invention, the guide vanes of a turbine engine guide vane array define a set of fluid flow passages having a chordwisely converging forward portion. The vane array also has a solidity sufficient to resist separation of fluid flowing through the passages.
In another embodiment the vanes cooperate to obstruct an observer's line of sight to a selected plane upstream of the vane array.
The foregoing and other features of the various embodiments of the invention will become more apparent from the following description of the best mode for carrying out the invention and the accompanying drawings.
Referring to
Referring additionally to
Each guide vane 28 has a leading end 52 with a leading edge 54 and a trailing end 56 with a trailing edge 58. A chord line 62, depicted only in
Referring to
Each neighboring pair of vanes defines a fluid flow passage 74 having an inlet plane 76. Each passage has a chordwisely converging forward portion 80, i.e. a portion that diminishes in area with increasing distance from the inlet plane, a diverging mid-portion 82 and an aft portion 84 that ideally is non-convergent.
The vane array has a spanwisely varying solidity, which is the local ratio of chord to pitch at any given spanwise location, where pitch is the circumferential separation 86 between neighboring vanes. The solidity of the inventive vane array is high enough to resist fluid separation from surfaces 44, 46, i.e. the high solidity prevents separation from occurring or encourages momentarily separated fluid to quickly re-attach to the surfaces. In the illustrated embodiment, the solidity is at least about 3.
Each vane has a leading end lateral thickness tLE and a trailing end lateral thickness tTE (
The fluid stream F approaches the vane array at an angle of incidence I that varies across a range of values. In the example of
As seen best in
For the vane array of
In the partial vane array of
In operation, fluid approaches the vane array at an incidence angle and with a Mach number, both of which can vary as a function of engine power. The thin leading end 52 of each vane allows the vane array to balance the competing interests of tolerating a satisfactorily wide variation in the incidence angle without unacceptably restricting the flow capacity of the turbine. The solidity of the array and the relative circumferential positioning of the leading and trailing ends obstruct an observer's line of sight to planes upstream of the vanes. The high solidity of the array and the chordwise convergence of the forward portions 80 of passages 74 resist fluid separation.
Although this invention has been shown and described with reference to a specific embodiment thereof, it will be understood by those skilled in the art that various changes in form and detail may be made without departing from the invention as set forth in the accompanying claims.
Claims
1. A turbine engine guide vane array, comprising:
- a set of spanwisely and chordwisely extending guide vanes;
- a fluid flow passage defined between neighboring vanes, each passage having a chordwisely converging forward portion; and
- the vane array having a solidity selected to resist fluid separation.
2. The vane array of claim 1 wherein each vane has a leading end thickness and a trailing end thickness and the leading end thickness is approximately equal to the trailing end thickness.
3. The vane array of claim 1 wherein the solidity is at least about 3.
4. The vane array of claim 1 wherein the vanes cooperate to obstruct an observer's line of sight to a selected plane upstream of the vane array.
5. The vane array of claim 1 wherein each vane has a leading end and a trailing end and the trailing end of each vane circumferentially overlaps the leading end of a neighboring vane over at least part of the vane span.
6. The vane array of claim 1 wherein each vane has a mean camber line and the mean camber line reverses curvature at least once over at least part of the vane span.
7. The vane array of claim 1 wherein each vane has a chord line, and a flowing fluid approaches the vane array at an incidence angle and a Mach number each subject to variation across respective ranges of values extending from a first incidence angle and a higher Mach number to a second incidence angle and a lower Mach number and wherein the chord line is more closely aligned with the higher Mach number end of the Mach number range than with the lower Mach number end of the Mach number range.
8. The vane array of claim 7 wherein the trailing edge of each vane is oriented approximately axially.
9. The vane array of claim 7 wherein each vane has a leading edge angle oriented within the range of incidence angles.
10. The vane array of claim 1 wherein the vanes have a trailing edge oriented so that the tip of the trailing edge is further aft than the root of the trailing edge.
11. A turbine engine stator vane having a leading end and a trailing end each having a lateral thickness, the lateral thickness of the leading end being approximately equal to the lateral thickness of the trailing end, the vane also having a mean camber line that reverses curvature at least once over at least part of the vane span.
12. The stator vane of claim 11 comprising a cast leading segment, a cast or sheet metal trailing segment and a pair of panels extending between the leading and trailing segments.
13. The stator vane of claim 12 wherein the panels are sheet metal panels.
14. The stator vane of claim 11 wherein the vane has a root, a tip, and a trailing edge, and the trailing edge is oriented so that when the vane is installed in an engine the vane tip at the trailing edge is further aft than the vane root at the trailing edge.
15. The stator vane of claim 11 wherein the trailing end is scarfed.
16. The stator vane of claim 11 comprising a leading segment, a trailing segment and panels extending chordwisely between the segments with the leading segment being substantially entirely chordwisely forward of the panels and the trailing segment being substantially entirely chordwisely aft of the panels.
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Type: Grant
Filed: Dec 21, 2004
Date of Patent: Mar 27, 2007
Patent Publication Number: 20060133930
Assignee: United Technologies Corporation (Hartford, CT)
Inventors: Andrew S. Aggarwala (East Hartford, CT), Richard E. Gacek (South Windsor, CT), Joel H. Wagner (Wethersfield, CT), Jeff S. Noall (South Windsor, CT), Timothy S. Snyder (Glastonbury, CT)
Primary Examiner: Hoang Nguyen
Attorney: Kenneth C. Baran
Application Number: 11/019,870
International Classification: F01D 1/02 (20060101);